Effects of High-Speed Tunnel Noise on Laminar-Turbulent Transition

Schneider, Steven P.

doi:10.2514/2.3705

Cited by 307 publications

(105 citation statements)

References 90 publications

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“…Analyses of the current data with standard linear stability methods indicates that the transition location corresponds to second-mode amplification factors e N with N ≈ 8-12 at transition onset [20,26]. These values, even those obtained before implementation of the cleaning regimen, are high compared to the more typical values of N ≈ 5-6 usually characterizing a "noisy" tunnel [2]. Although the transition N factors recorded early in the current test campaign were higher than expected for a noisy tunnel, there was a larger than desired scatter in results.…”

Section: Introductionmentioning

confidence: 96%

“…Hypersonic wind tunnels exist where there are low disturbance levels, such as those at Purdue University [2][3][4] and Texas A&M University [5,6]. Currently, the parameter space available to lowdisturbance hypersonic wind tunnels does not permit the study of the interaction of boundary-layer instability and thermochemistry, which is important for accurately modeling realistic reentry flows; this is because low-disturbance hypersonic tunnels have a low-ordered kinetic energy, or total enthalpy, in the freestream relative to relevant chemical or vibrational energy levels.…”

Section: Introductionmentioning

confidence: 99%

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Effects of Shock-Tube Cleanliness on Hypersonic Boundary Layer Transition at High Enthalpy

et al. 2017

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Section: Introductionmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

Effects of Shock-Tube Cleanliness on Hypersonic Boundary Layer Transition at High Enthalpy

et al. 2017

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“…On the experimental side, the presence of inherent noise in high-speed wind tunnels make them unreliable predictors of fight performance, except in special cases [1]. In flight conditions, the sources of such ''noise'' may be different; for example, random disturbances may arise due to turbulence or due to other local small-scale events such as microbursts.…”

Section: Introductionmentioning

confidence: 97%

Predicting shock dynamics in the presence of uncertainties

Lin

Karniadakis

2006

Journal of Computational Physics

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“…This led the disturbances possessed in the facilities to induce bypass type of transitions, which would take place much earlier than those obtained in flight conditions. In addition, the transition mechanisms stemmed from small-disturbance environments can be altered or bypassed altogether in high-noise environments [11]. Quiet tunnels, with laminar velocity profiles near the wall, can produce a noise environment close to the flight conditions, and hence are more reliable.…”

mentioning

confidence: 99%

A Favré averaged transition prediction model for hypersonic flows

Song

Lee

2010

Sci. China Technol. Sci.

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Transition prediction is crucial for aerothermodynamic and thermal protection system design of hypersonic vehicles. The compressible form of laminar kinetic energy equation is derived based on Favré average formality in the present paper. A closure of the equation is deduced and simplified under certain hypotheses and scaling analysis. A laminar-to-turbulent transition prediction procedure is proposed for high Mach number flows based on the modeled Favré-averaged laminar kinetic energy equation, in conjunction with the Favré-averaged Navier-Stokes equations. The proposed model, with and without associated explicit compressibility terms, is then applied to simulate flows over flared-cones with a free-stream Mach number of 5.91, and the onset locations of the boundary layer transition under different wall conditions are estimated. The computed onset locations are compared with those obtained by the model based on a compressibility correction deduced from the reference-temperature concept, together with experimental data. It is revealed that the present model gives a more favorable transition prediction for hypersonic flows. transition prediction, laminar fluctuation, hypersonic, compressibility Citation: Song B, Lee C H. A Favré averaged transition prediction model for hypersonic flows.Boundary layer transition profoundly affects the aerodynamic and thermal characteristics of hypersonic vehicles, thus the transition prediction is crucial for aerothermodynamic and thermal protection system design [1]. Although stability and transition of boundary layers of supersonic and hypersonic speeds has been studied for a century, no comprehensive theory on boundary layer transition process is established, especially for hypersonic flows for their extreme complexity. Transition is influenced by many factors, such as the local Mach number, Reynolds number per unit length, pressure gradients, nosetip bluntness (including the entropy swallowing effects), crossflow effects, surface roughness, wall cooling, suction and blowing effects, even high temperature/nonequilibrium effects if the flow is pyrochemical [2]. The effects of these factors are coupled and difficult to analyze.Among the common engineering approaches for transition prediction, the e N method can describe the initial linear growing stage of small disturbances reliably, but it is unable to cover the entire course of the transition. Furthermore, it is impossible to correlate the experiment data with a unique N for hypersonic flows. The empirical formulations are relatively simple and easy to execute, but each of them is restricted within certain types of flows, and can not function universally. For example, the criterion Re θ /M e = constant deduced from hypersonic flights was proven to fail when it is used to correlate the wind tunnel data [3]. Transition criteria based on the skin friction and heat transfer rate distributions are affected by the quality of computational grids near the wall, yet they are not applicable under the presence of pressure gradients.Numerica...

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Effects of High-Speed Tunnel Noise on Laminar-Turbulent Transition

Cited by 307 publications

References 90 publications

Effects of Shock-Tube Cleanliness on Hypersonic Boundary Layer Transition at High Enthalpy

Effects of Shock-Tube Cleanliness on Hypersonic Boundary Layer Transition at High Enthalpy

Predicting shock dynamics in the presence of uncertainties

A Favré averaged transition prediction model for hypersonic flows

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